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Research of BeidouII/SINS Integrated Navigation System

Dai Hai-xia

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Abstract

Apply the application of Pseudo-range and Pseudo-range rate integrated model to BeidouⅡ/SINS,which use the ephemeris of satellite and the positon,velocity given by SINS calculate relevant Pseudo-range and Pseudo-range rate,then compare this with receiver given, attain the error as measurement value. Estimating error of BeidouII satellite position system and SINS by Kalman filter to realize error emendation for system. State and measurement model of integrated navigation are establishment.Simulation results show this integrated model can receive very high navigation accuracy.

About this research paper

What this paper is about

Apply the application of Pseudo-range and Pseudo-range rate integrated model to BeidouⅡ/SINS,which use the ephemeris of satellite and the positon,velocity given by SINS calculate relevant Pseudo-range and Pseudo-range rate,then compare this with receiver given, attain the error as measurement value. Estimating error of BeidouII satellite position system and SINS by Kalman filter to realize error emendation for system. State and measurement model of integrated navigation are establishment.Simulation results show this integrated model can receive very high navigation accuracy.

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Available abstract

Apply the application of Pseudo-range and Pseudo-range rate integrated model to BeidouⅡ/SINS,which use the ephemeris of satellite and the positon,velocity given by SINS calculate relevant Pseudo-range and Pseudo-range rate,then compare this with receiver given, attain the error as measurement value. Estimating error of BeidouII satellite position system and SINS by Kalman filter to realize error emendation for system. State and measurement model of integrated navigation are establishment.Simulation results show this integrated model can receive very high navigation accuracy.

Key concepts: Ephemeris, Kalman filter, Navigation system, Range (aeronautics), Pseudorange, Computer science, Satellite navigation, Satellite

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